Patents by Inventor Jerome Huber
Jerome Huber has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Publication number: 20230227150Abstract: An aircraft landing gear 100 includes a structural main leg 110, having a substantially circular cross-section and defining a front side for facing upstream in use and a rear side for facing downstream in use. The landing gear includes a shaped element 151 attached to an attachment point located on the rear side of the structural main leg. The shaped element extends rearwards from the structural main leg to provide a combined cross-sectional shape of the structural main leg and shaped element that is elongated in the upstream-downstream direction compared to the structural main leg.Type: ApplicationFiled: November 22, 2022Publication date: July 20, 2023Inventors: Jerome HUBER, Aline SCOTTO, Maxime ITASSE, Robert NORTHAM
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Patent number: 11292575Abstract: In the field of aeronautics, there is disclosed an aircraft with reduced installation noise and specifically an aircraft wing and jet engine system including an aircraft wing and at least one jet engine with high bypass ratio attached to the wing, suitable for emitting a jet intercepted by a first portion of the trailing edge of the wing. The range formed by the set of angles with orientation ? defined by a vector following the direction of the jet and by a vector following the tangent at a point of the first portion of the trailing edge and oriented towards the wing tip of the wing, is included within a range of angles selected from the range delimited by 5° and 65°, and the range delimited by 115° and 175°.Type: GrantFiled: June 17, 2016Date of Patent: April 5, 2022Assignee: CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUEInventors: Peter Jordan, Andre Cavalieri, William Wolf, Selene Piantanida, Vincent Jaunet, Jerome Huber
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Publication number: 20180222568Abstract: In the field of aeronautics, there is disclosed an aircraft with reduced installation noise and specifically an aircraft wing and jet engine system including an aircraft wing and at least one jet engine with high bypass ratio attached to the wing, suitable for emitting a jet intercepted by a first portion of the trailing edge of the wing. The range formed by the set of angles with orientation ? defined by a vector following the direction of the jet and by a vector following the tangent at a point of the first portion of the trailing edge and oriented towards the wing tip of the wing, is included within a range of angles selected from the range delimited by 5° and 65°, and the range delimited by 115° and 175°.Type: ApplicationFiled: June 17, 2016Publication date: August 9, 2018Inventors: Peter JORDAN, Andre CAVALIERI, William WOLF, Selene PIANTANIDA, Vincent JAUNET, Jerome HUBER
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Patent number: 9151244Abstract: An aircraft jet engine comprising a nozzle to eject a gas stream, and a system for reducing the noise generated by the ejection of the gas stream. This system comprises several ducts which each are connected upstream to a recess divided into several chambers and open, downstream, at the outlet of nozzle. In this way, each duct ejects a fluid jet deriving from the recess and which interacts with the gas stream of the engine. The system also comprises a pulsation means for the fluid jet which brings about its ejection at the nozzle outlet and/or modulates its speed by varying the volume contained in the recess.Type: GrantFiled: January 24, 2012Date of Patent: October 6, 2015Assignees: AIRBUS Operations (S.A.S.), CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, UNIVERSITE DE POITIERSInventors: Jerome Huber, Jean Paul Bonnet, Luis Gomes, Remy Maury
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Publication number: 20150219013Abstract: A turbomachine assembly comprising a device that attenuates noise by ejecting jets of fluid, this device comprising fluid supply ducts, fluid ejection tubes and a distribution duct of annular shape. The distribution duct is connected firstly to inlets of the ejection tubes and secondly to outlets of the fluid supply ducts so as to create a flow path for the circulation of fluid from the inlets of the fluid supply ducts to the outlets of the ejection tubes.Type: ApplicationFiled: July 21, 2014Publication date: August 6, 2015Inventors: Jerome Huber, Arnaud Hormiere, Lois Dussol, Clemence Barthomeuf, Au Dax, Florent Bonneau
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Patent number: 8887489Abstract: According to the invention, the shape of each of said chevrons is defined: by two lateral sides (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when moving away from the latter, converge towards each other without joining so that the rear ends (21R, 22R) of said lateral walls (21, 22) are spaced from each other; and by a curvilinear transverse line (23.1) connecting the rear ends (21R, 22R) of said lateral walls (21, 22) by forming two rounded side protrusions (24.1, 25.1) separated by an intermediate rounded recess (26.1).Type: GrantFiled: August 4, 2008Date of Patent: November 18, 2014Assignee: Airbus Operations (SAS)Inventors: Amadou André Sylla, Jérôme Huber, Olivier Pelagatti, Damien Prat, Klaus Debatin
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Patent number: 8770921Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.Type: GrantFiled: March 31, 2009Date of Patent: July 8, 2014Assignees: Airbus Operations S.A.S., Centre National de la Recherche Scientifique (CNRS), Université de PoitiersInventors: Jerome Huber, Jean-Paul Bonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Patent number: 8516824Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.Type: GrantFiled: August 21, 2008Date of Patent: August 27, 2013Assignee: Airbus Operations S.A.S.Inventors: Frederic Journade, Jerome Journade, Jerome Huber
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Patent number: 8393139Abstract: An aircraft jet engine including a wall centered about a longitudinal axis and surrounding a stream of gas ejected at a downstream end of the wall in the direction of the axis, primary ducts distributed at the periphery of the downstream end of the wall configured on command each to eject a jet of primary fluid to interact with the ejected stream of gas, the primary ducts of each pair converging towards one another near the downstream end of the wall so that the primary jets ejected form two sides of a triangle that meet at the vertex thereof in a view projected onto a plane perpendicular to a transverse plane, and secondary ducts each associated with each pair of primary ducts and configured on command to eject a jet of secondary fluid directed into the triangle formed by the primary jets.Type: GrantFiled: March 31, 2009Date of Patent: March 12, 2013Assignees: Airbus Operations (S.A.S.), Centre National de la Recherche Scientifique (CNRS), Universite de PoitiersInventors: Jerome Huber, Jean-Paul Bonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Publication number: 20120186224Abstract: The invention relates to an aircraft jet engine comprising a nozzle (2) intended to eject a gas stream, and a system for reducing the noise (3) generated by the ejection of the gas stream. This system comprises several ducts (11a) which each, on the one hand, are connected upstream to a recess divided into several chambers and, on the other hand, open, downstream, at the outlet of nozzle (2). In this way, each duct ejects a fluid jet deriving from the recess and which interacts with the gas stream of the engine. The system also comprises a pulsation means (12) for the fluid jet which brings about its ejection at the nozzle outlet and/or modulates its speed by varying the volume contained in the recess. The system is configured in particular for balancing static pressures between the chambers.Type: ApplicationFiled: January 24, 2012Publication date: July 26, 2012Applicants: Airbus Operations (S.A.S.), UNIVERSITE DE POITIERS, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUEInventors: Jerome Huber, Jean Paul Bonnet, Luis Gomes, Remy Maury
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Patent number: 8157050Abstract: A jet engine, including a wall surrounding a first gas flow ejected from a downstream end of the wall along a longitudinal axis, a second flow of gas running outside the wall in a direction of ejection of the first gas flow, at least one duct arranged on the periphery of the downstream end of the wall which is desired to eject a gas flow for interacting with one and/or the other gas flow, the at least one duct including a terminal section provided at the free end thereof with an outlet opening through which the fluid is ejected. The terminal section successively includes a first section of straight duct aligned along a median axis and a second duct section forming a bend relative to the straight section, the second portion having a free end provided with the outlet opening and sufficiently close to the median axis of the first section to give the terminal section a reduced restriction in a direction of formation of the bend.Type: GrantFiled: March 31, 2009Date of Patent: April 17, 2012Assignees: Airbus Operations (S.A.S.), Centre National de la Recherche Scientifique (CNRS), Universitéde PoitiersInventors: Jerome Huber, Jean-Paul Bonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Patent number: 8132756Abstract: An aircraft engine having a longitudinal axis, including a wall surrounding a gas stream that is ejected at a downstream end of the wall along the longitudinal axis, wherein a plurality of conduits distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an outlet orifice, a fluid jet in the form of a sheet, in such a way that the jets thus ejected each form a fluid perturbation around the ejected gas stream.Type: GrantFiled: March 31, 2009Date of Patent: March 13, 2012Assignees: Centre National de la Recherche Scientifique (CNRS), Universite de Poitiers, Airbus Operations SASInventors: Jerome Huber, Jean-Paul Bonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Publication number: 20110203254Abstract: A gas ejection cone for an aircraft turbojet, the cone including a hollow main body defining, on the outside, a radially inner skin of an annular primary flow channel, and a device generating turbulence in the primary flow limiting jet noise, mounted so as to move on the main body so as to be able to be displaced from an extracted position in which the device projects toward downstream in relation to a downstream end of the hollow main body, and a retracted position in which the device is retracted into the hollow main body, and vice versa. Further, the device includes a cylindrical support body having an axis parallel to an axis of the ejection cone, and at least one fin supported by the body.Type: ApplicationFiled: August 21, 2008Publication date: August 25, 2011Applicant: Airbus Operations (inc. as a Soc. par Act. Simpl.)Inventors: Frederic Journade, Jerome Journade, Jerome Huber
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Publication number: 20110192167Abstract: According to the invention, the shape of each of said chevrons is defined: by two lateral sides (21, 22) having front ends (21A, 22A) that are connected to said nozzle (4, 10) and that, when moving away from the latter, converge towards each other without joining so that the rear ends (21R, 22R) of said lateral walls (21, 22) are spaced from each other; and by a curvilinear transverse line (23.1) connecting the rear ends (21R, 22R) of said lateral walls (21, 22) by forming two rounded side protrusions (24.1, 25.1) separated by an intermediate rounded recess (26.1).Type: ApplicationFiled: August 4, 2008Publication date: August 11, 2011Applicant: Airbus Operations (SAS)Inventors: Amadou André Sylla, Jérôme Huber, Olivier Pelagatti, Damien Prat, Klaus Debatin
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Publication number: 20110047960Abstract: The invention relates to a dual-flow turbine engine for an aircraft with low noise emission, wherein the opening (6) for the cold flow (9) of the turbine engine is provided with short, narrow, and spaced chevrons (15) that penetrate deeply, like claws, into said cold flow (9).Type: ApplicationFiled: April 30, 2009Publication date: March 3, 2011Applicants: AIRBUS OPERATIONS (SAS)Inventors: Jérôme Huber, Klaus Debatin, Amadou André, Olivier Pelagatti
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Publication number: 20110042162Abstract: A jet engine, including a wall surrounding a first gas flow ejected from a downstream end of the wall along a longitudinal axis, a second flow of gas running outside the wall in a direction of ejection of the first gas flow, at least one duct arranged on the periphery of the downstream end of the wall which is desired to eject a gas flow for interacting with one and/or the other gas flow, the at least one duct including a terminal section provided at the free end thereof with an outlet opening through which the fluid is ejected. The terminal section successively includes a first section of straight duct aligned along a median axis and a second duct section forming a bend relative to the straight section, the second portion having a free end provided with the outlet opening and sufficiently close to the median axis of the first section to give the terminal section a reduced restriction in a direction of formation of the bend.Type: ApplicationFiled: March 31, 2009Publication date: February 24, 2011Applicants: AIRBUS OPERATIONS (inc. as a Soc.par Act. Simpl.), CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE(CNRS), UNIVERSITE DE POITIERSInventors: Jerome Huber, Jean-Paul Bonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Publication number: 20110030341Abstract: An aircraft jet engine including a wall centered about a longitudinal axis and surrounding a stream of gas ejected at a downstream end of the wall in the direction of the axis, primary ducts distributed at the periphery of the downstream end of the wall configured on command each to eject a jet of primary fluid to interact with the ejected stream of gas, the primary ducts of each pair converging towards one another near the downstream end of the wall so that the primary jets ejected form two sides of a triangle that meet at the vertex thereof in a view projected onto a plane perpendicular to a transverse plane, and secondary ducts each associated with each pair of primary ducts and configured on command to eject a jet of secondary fluid directed into the triangle formed by the primary jets.Type: ApplicationFiled: March 31, 2009Publication date: February 10, 2011Applicants: AIRBUS OPERATIONS(inc as a Societe par Act Simpl.), CENTRE NATIONAL DE LA RECHERCHE SCIENT. (CNRS), UNIVERSITE DE POITIERSInventors: Jerome Huber, Jean-Paul Nonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Publication number: 20110027070Abstract: An aircraft jet engine with a longitudinal axis, including a wall enclosing a gas flow ejected from a downstream end of the wall in the longitudinal axis, plural ducts being distributed around the periphery of the downstream end of the wall each including a terminal section, including an outlet opening. Each duct can eject a fluid jet through the outlet opening thereof. The ducts are configured to eject the fluid jets essentially parallel to each other, each fluid jet ejected through the corresponding outlet opening forming a lateral angle with the longitudinal axis in a projection view in a plane with the longitudinal axis.Type: ApplicationFiled: March 31, 2009Publication date: February 3, 2011Applicants: AIRBUS OPERATIONS, Centre National De La Recherche Scienti (CNRS), UNIVERSITE DE POITERSInventors: Jerome Huber, Jean-Paul Bonnet, Joel Delville, Peter Jordan, Francois Strekowski
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Publication number: 20100065680Abstract: The invention relates to an aircraft engine having a longitudinal axis (XX?), comprising a wall (30) surrounding a gas stream that is ejected at a downstream end (30a) of the wall along the longitudinal axis, characterized in that a plurality of conduits (60, 62, 64, 66, 68, 70, 72, 74) distributed at the periphery of the downstream end of the wall are each capable of ejecting, via an outlet orifice (60c), a fluid jet (76) in the form of a sheet, in such a way that the jets thus ejected each form a fluid perturbation around the ejected gas stream.Type: ApplicationFiled: March 31, 2009Publication date: March 18, 2010Applicants: Airbus France, CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE ( CNRS ), UNIVERSITE DE POITIERSInventors: Jerome HUBER, Jean-Paul BONNET, Joel DELVILLE, Peter JORDAN, Francois STREKOWSKI
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Patent number: 7117619Abstract: A two-sided, multi-sport scoring banner 30 consisting of a plurality of flexible scoring elements 44A, 44B, 44C, 44D sandwiched between a front face 32 and a back face 34. A set of scoring symbols 44A, 44B, 44C, 44D selectively positioned and uniformly spaced upon the scoring element to allow the score of a competitive event to be displayed through a plurality of windows 48, 50, 52, 54 formed into the front and back faces of the scoring banner. A plurality of utility storage pockets 90, a plurality of equipment storage loops 110 and a plurality of hooks 120 attached to the scoring banner to facilitate the organization of a variety of sport equipment items. A team insignia 74, a home and visitor title 76, 78 and a plurality of advertisement signs 130 printed on or attached to the scoring banner's two faces. In one embodiment a plurality of linear pockets 60, 62, 64, 66 are included within the scoring banner to facilitate the use and storage of a plurality of ground stakes or rods 58.Type: GrantFiled: November 21, 2003Date of Patent: October 10, 2006Inventor: John Jerome Huber